HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 500,000 Max Cl/Cd: 78.93 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2010-il-500000-n5.txt Download as CSV file: xf-hq2010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7164 0.04154 0.03899 -0.0587 1.0000 0.0041
-10.000 -0.7313 0.03701 0.03417 -0.0582 1.0000 0.0041
-9.750 -0.7435 0.03226 0.02901 -0.0566 1.0000 0.0041
-9.500 -0.7350 0.03059 0.02720 -0.0553 1.0000 0.0043
-9.250 -0.7212 0.02782 0.02411 -0.0555 0.9969 0.0044
-9.000 -0.6963 0.02559 0.02161 -0.0571 0.9903 0.0045
-8.750 -0.6689 0.02346 0.01918 -0.0588 0.9852 0.0048
-8.500 -0.6422 0.02153 0.01695 -0.0601 0.9791 0.0050
-8.250 -0.6124 0.02021 0.01541 -0.0614 0.9736 0.0054
-8.000 -0.5839 0.01894 0.01391 -0.0624 0.9669 0.0058
-7.750 -0.5540 0.01798 0.01273 -0.0634 0.9601 0.0062
-7.500 -0.5264 0.01672 0.01125 -0.0639 0.9517 0.0065
-7.250 -0.4995 0.01530 0.00964 -0.0644 0.9431 0.0070
-7.000 -0.4729 0.01452 0.00876 -0.0645 0.9332 0.0074
-6.750 -0.4463 0.01390 0.00803 -0.0645 0.9240 0.0079
-6.500 -0.4201 0.01329 0.00730 -0.0643 0.9153 0.0085
-6.250 -0.3945 0.01273 0.00663 -0.0640 0.9063 0.0090
-6.000 -0.3686 0.01229 0.00606 -0.0637 0.8981 0.0097
-5.750 -0.3434 0.01172 0.00538 -0.0633 0.8894 0.0109
-5.500 -0.3177 0.01129 0.00489 -0.0629 0.8804 0.0122
-5.250 -0.2916 0.01095 0.00445 -0.0626 0.8722 0.0136
-5.000 -0.2653 0.01062 0.00404 -0.0623 0.8643 0.0155
-4.750 -0.2388 0.01029 0.00369 -0.0621 0.8579 0.0204
-4.500 -0.2121 0.01002 0.00341 -0.0619 0.8514 0.0283
-4.000 -0.1579 0.00960 0.00294 -0.0617 0.8396 0.0416
-3.750 -0.1307 0.00941 0.00273 -0.0616 0.8336 0.0494
-3.500 -0.1036 0.00919 0.00253 -0.0615 0.8275 0.0626
-3.250 -0.0765 0.00896 0.00233 -0.0614 0.8210 0.0827
-3.000 -0.0494 0.00871 0.00215 -0.0613 0.8148 0.1107
-2.750 -0.0227 0.00840 0.00198 -0.0613 0.8078 0.1583
-2.250 0.0306 0.00770 0.00165 -0.0612 0.7939 0.2908
-2.000 0.0566 0.00725 0.00151 -0.0611 0.7867 0.3957
-1.750 0.0830 0.00695 0.00144 -0.0609 0.7784 0.4789
-1.500 0.1095 0.00675 0.00141 -0.0606 0.7686 0.5455
-1.250 0.1364 0.00667 0.00138 -0.0603 0.7574 0.5853
-1.000 0.1632 0.00661 0.00137 -0.0600 0.7453 0.6228
-0.500 0.2177 0.00659 0.00134 -0.0595 0.7216 0.6636
-0.250 0.2451 0.00661 0.00133 -0.0593 0.7089 0.6779
0.000 0.2723 0.00662 0.00134 -0.0591 0.6966 0.6933
0.250 0.2996 0.00664 0.00135 -0.0589 0.6842 0.7078
0.500 0.3269 0.00669 0.00136 -0.0587 0.6700 0.7184
0.750 0.3542 0.00673 0.00137 -0.0585 0.6564 0.7265
1.000 0.3817 0.00678 0.00140 -0.0584 0.6442 0.7348
1.250 0.4089 0.00683 0.00144 -0.0582 0.6304 0.7435
1.500 0.4360 0.00690 0.00148 -0.0580 0.6144 0.7522
2.000 0.4896 0.00707 0.00159 -0.0575 0.5793 0.7708
2.250 0.5161 0.00719 0.00168 -0.0572 0.5565 0.7805
2.500 0.5421 0.00733 0.00176 -0.0569 0.5317 0.7908
2.750 0.5678 0.00750 0.00187 -0.0564 0.5043 0.8017
3.000 0.5928 0.00771 0.00201 -0.0559 0.4673 0.8133
3.250 0.6165 0.00803 0.00217 -0.0552 0.4193 0.8262
3.500 0.6403 0.00835 0.00237 -0.0545 0.3786 0.8408
3.750 0.6633 0.00870 0.00258 -0.0537 0.3307 0.8582
4.000 0.6851 0.00908 0.00282 -0.0526 0.2844 0.8834
4.250 0.7119 0.00934 0.00306 -0.0525 0.2533 0.9344
4.500 0.7465 0.00958 0.00328 -0.0542 0.2361 1.0000
4.750 0.7724 0.00983 0.00349 -0.0540 0.2232 1.0000
5.000 0.7980 0.01011 0.00371 -0.0537 0.2067 1.0000
5.250 0.8230 0.01043 0.00398 -0.0534 0.1869 1.0000
5.500 0.8474 0.01082 0.00425 -0.0530 0.1595 1.0000
5.750 0.8694 0.01146 0.00463 -0.0523 0.1131 1.0000
6.000 0.8917 0.01207 0.00506 -0.0516 0.0815 1.0000
6.250 0.9153 0.01253 0.00544 -0.0510 0.0650 1.0000
6.500 0.9389 0.01298 0.00586 -0.0505 0.0522 1.0000
6.750 0.9622 0.01345 0.00627 -0.0499 0.0410 1.0000
7.000 0.9856 0.01389 0.00668 -0.0493 0.0340 1.0000
7.250 1.0096 0.01427 0.00708 -0.0488 0.0296 1.0000
7.500 1.0323 0.01476 0.00754 -0.0482 0.0227 1.0000
7.750 1.0551 0.01523 0.00800 -0.0475 0.0172 1.0000
8.000 1.0769 0.01579 0.00857 -0.0467 0.0109 1.0000
8.250 1.0973 0.01649 0.00925 -0.0458 0.0058 1.0000
8.500 1.1179 0.01715 0.00994 -0.0448 0.0047 1.0000
8.750 1.1384 0.01779 0.01065 -0.0437 0.0040 1.0000
9.000 1.1587 0.01841 0.01136 -0.0427 0.0037 1.0000
9.250 1.1783 0.01907 0.01211 -0.0417 0.0034 1.0000
9.500 1.1967 0.01982 0.01296 -0.0404 0.0032 1.0000
9.750 1.2146 0.02056 0.01380 -0.0391 0.0031 1.0000
10.000 1.2311 0.02138 0.01476 -0.0376 0.0030 1.0000
10.250 1.2463 0.02226 0.01574 -0.0360 0.0029 1.0000
10.500 1.2577 0.02324 0.01684 -0.0338 0.0027 1.0000
10.750 1.2661 0.02434 0.01805 -0.0312 0.0026 1.0000
11.000 1.2736 0.02549 0.01932 -0.0287 0.0026 1.0000
11.250 1.2776 0.02691 0.02088 -0.0260 0.0025 1.0000
11.500 1.2760 0.02881 0.02294 -0.0230 0.0023 1.0000
11.750 1.2817 0.03022 0.02448 -0.0211 0.0023 1.0000
12.000 1.2853 0.03187 0.02626 -0.0192 0.0023 1.0000
12.250 1.2882 0.03365 0.02817 -0.0176 0.0023 1.0000
12.500 1.2887 0.03575 0.03041 -0.0161 0.0022 1.0000
12.750 1.2887 0.03799 0.03279 -0.0149 0.0022 1.0000
13.000 1.2880 0.04047 0.03543 -0.0140 0.0022 1.0000
13.250 1.2843 0.04339 0.03854 -0.0134 0.0021 1.0000
13.500 1.2806 0.04647 0.04176 -0.0132 0.0021 1.0000
13.750 1.2740 0.05014 0.04559 -0.0135 0.0021 1.0000
14.000 1.2665 0.05415 0.04977 -0.0142 0.0021 1.0000
14.250 1.2572 0.05870 0.05448 -0.0156 0.0021 1.0000
14.500 1.2467 0.06376 0.05970 -0.0175 0.0021 1.0000
14.750 1.2341 0.06955 0.06566 -0.0201 0.0021 1.0000
15.000 1.2212 0.07585 0.07212 -0.0233 0.0021 1.0000
15.250 1.2047 0.08326 0.07971 -0.0273 0.0021 1.0000
15.500 1.1891 0.09097 0.08758 -0.0316 0.0021 1.0000
15.750 1.1728 0.09908 0.09583 -0.0362 0.0021 1.0000
16.000 1.1548 0.10786 0.10477 -0.0412 0.0021 1.0000
16.250 1.1375 0.11666 0.11369 -0.0462 0.0021 1.0000
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